Improved computer program for calculation of viscous-inviscid interactions

Report (1973)
Copyright: © 1973 Von Karman Institute for Fluid Dynamics
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Published Date

01-03-1973

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VKI Training Center for Experimental Aerodynamics Technical Note 82

Abstract

This report describes a theoretical and experimental investigation of the effect of wall cooling • on the overall features of shock wave laminar boundary layer interactions in hypersonic two dimensional flow. The integral metho4 of Lees-Reeves-Klineberg has been modified in order to compute viscous interactions over a continuous range of wall-to-stagnation temperature ratios using a single set of "universal" integral functions. Comparisons between the theoretical predictions and the experimental results obtained from pressure and heat transfer distribution measurements show satisfactory agreements. These experiments have been carried out in a moderately hypersonic flow (M = 6) over flat plate-wedge models for different wall cooling rates, corresponding to conditions lying between a highly cooled wall and a quasi-adiabatic surface. Furthermore, the theory developed herein may be considered to be a significant improvement in the attempt to calculate viscous interactions where the wall temperature distribution is prescribed.